U.S. patent application number 14/220935 was filed with the patent office on 2014-09-11 for window module for an aircraft or spacecraft.
The applicant listed for this patent is AIRBUS OPERATIONS GMBH. Invention is credited to HANS-ACHIM BAUER, ANDRE ZYBALA.
Application Number | 20140253012 14/220935 |
Document ID | / |
Family ID | 47878549 |
Filed Date | 2014-09-11 |
United States Patent
Application |
20140253012 |
Kind Code |
A1 |
BAUER; HANS-ACHIM ; et
al. |
September 11, 2014 |
WINDOW MODULE FOR AN AIRCRAFT OR SPACECRAFT
Abstract
The present disclosure pertains to a window module for an
aircraft or spacecraft, including a window frame which comprises,
at least in portions, a current-generating element for generating
an electric current.
Inventors: |
BAUER; HANS-ACHIM; (Hamburg,
DE) ; ZYBALA; ANDRE; (Hanstedt, DE) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
AIRBUS OPERATIONS GMBH |
Hamburg |
|
DE |
|
|
Family ID: |
47878549 |
Appl. No.: |
14/220935 |
Filed: |
March 20, 2014 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
PCT/EP2012/068908 |
Sep 26, 2012 |
|
|
|
14220935 |
|
|
|
|
61541498 |
Sep 30, 2011 |
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Current U.S.
Class: |
320/101 ;
136/259 |
Current CPC
Class: |
B64D 11/00155 20141201;
Y02E 10/50 20130101; H02J 7/35 20130101; B64C 1/1492 20130101; Y02T
50/50 20130101; B64D 11/0015 20130101; B64D 2211/00 20130101; H02S
20/00 20130101 |
Class at
Publication: |
320/101 ;
136/259 |
International
Class: |
B64C 1/14 20060101
B64C001/14; H02J 7/35 20060101 H02J007/35; H01L 31/042 20060101
H01L031/042 |
Foreign Application Data
Date |
Code |
Application Number |
Sep 30, 2011 |
DE |
10 2011 083 810.4 |
Claims
1. A window module for an aircraft or spacecraft, comprising a
window frame which comprises, at least in portions, a
current-generating element for generating an electric current.
2. The window module according to claim 1, wherein the
current-generating element is arranged in the region of the inner
surface of the window frame.
3. The window module according to claim 1, wherein the
current-generating element generates the electric current by a
photoelectric element.
4. The window module according to claim 1, wherein the
current-generating element is a polymeric organic solar cell.
5. The window module according to claim 4, wherein the geometric
configuration of the current-generating element is substantially
identical to the geometric configuration of the associated
underlying region of the window frame.
6. The window module according to claim 1, wherein the window
module comprises an interface for transmitting the electric current
generated by the current-generating element to an electronic
device.
7. The window module according to claim 6, comprising a controller
to control the charging process for the electronic device and/or an
electrical storage unit are further provided on the window
frame.
8. The window module according to claim 7, wherein the interface
for transmitting the generated electric current is arranged in the
lower region of the window frame.
9. The window module according to claim 1, wherein the window
module is of a modular construction, consisting of the individual
components.
10. The window module according to claim 1, wherein the thickness
of the current-generating element is considerably less than the
respective thickness of the associated region of the window
frame.
11. The window module according to claim 1, wherein a window pane
is further provided, of which the material properties are selected
in such a way that the absorption of the wavelength, which the
energy generation in the current-generating element causes, of the
light entering during operation is as low as possible.
12. The window module according to claim 1, wherein the mechanical
interfaces for connecting the window module to the aircraft or
spacecraft correspond to the mechanical interfaces which are
conventionally used for a window module.
13. The window module according to claim 1, wherein the
current-generating element comprises lenses for focusing and
amplifying the incident light.
14. An aircraft or spacecraft having at least one window module
according to claim 1.
Description
CROSS-REFERENCES TO RELATED APPLICATIONS
[0001] This application is a continuation of and claims priority to
PCT/EP2012/068908 filed Sep. 26, 2012, which claims the benefit of
and priority to U.S. Provisional Application No. 61/541,498, filed
Sep. 30, 2011 and German Patent Application No. 10 2011 083 810.4,
filed Sep. 30, 2011, the entire disclosures of which are herein
incorporated by reference.
TECHNICAL FIELD
[0002] The present invention relates to a window module for an
aircraft or spacecraft.
[0003] Although applicable to any window modules in an aircraft or
spacecraft, the present invention and the problem on which it is
based will be explained in detail with reference to an
aircraft.
BACKGROUND
[0004] In the aircraft cabin, there is usually the possibility to
provide passengers with the opportunity to charge electronic
devices at their seat through the electrical on-board network. For
this purpose, there is a universal socket at the seat which
provides a voltage of 110 V. This socket is configured in such a
way that it is suitable for the operation of laptops having a power
of approximately 50-70 W. Connecting said socket to the electrical
on-board network of the aircraft requires wiring of the seat,
whereby, when exchanging the seat or changing the seat
configuration in the aircraft cabin, all of the cable connections
have to be disconnected and then reconnected again.
[0005] Furthermore, in recent years laptops have begun to be
increasingly replaced by tablet PCs, such as the iPad, or by
smartphones. This category of high-powered but energy-saving
devices is referred to as what are known as personal electronic
devices (PEDs).
[0006] From the prior art according to DE 10 2005 002 545 A1, an
energy buffer device in an aircraft is known, by means of which
electronic devices, which are usually only in operation for a short
amount of time, can be operated independently. However, this is
disadvantageous in that the energy buffer device has to be
connected via the electrical on-board network of the aircraft for
charging its energy storage unit, whereby a cable connection is
required for connecting to the electrical on-board network.
[0007] Furthermore, from the prior art according to DE 10 2005 046
729 A1, an energy supply system is known in which energy is
supplied to an electrical consumer via a fuel cell. However, this
is disadvantageous in that an energy supply system of this type can
in turn be used as a central system for providing electrical energy
for the electrical on-board network, which has to be connected to
the seats in the aircraft cabin via cables in a known manner.
SUMMARY
[0008] It is therefore an idea of the present invention to provide
a device for charging or electrically operating electronic devices
for an aircraft or a spacecraft, which device can be easily
retrofitted or exchanged independently of the electrical on-board
network.
[0009] According thereto, a window module comprising a window frame
is provided, which window frame comprises a current-generating
element for generating an electric current.
[0010] The idea on which the present invention is based consists in
using the hitherto unused region of the window frame for generating
electric current and using this for charging and/or operating an
electronic device, whereby the burden on the electrical on-board
network of the aircraft is relieved. In particular, the incident
sunlight and/or the light from the cabin illumination system can be
used for generating the electric current.
[0011] An advantage of the present invention is that the present
window module provides an energy source for electronic devices
having a low electrical power, which energy source is independent
of the aircraft infrastructure and therefore is not connected to
the electrical on-board network of the aircraft. In addition, the
cable connection at the seat for connecting to the electrical
on-board network can advantageously be omitted, whereby refitting
seats in another seat arrangement or exchanging seats is made
easier.
[0012] Furthermore, the present invention advantageously allows the
associated control electronics for the current-generating element
to be integrated into the region of the aircraft inner lining,
which at the same time is a component of the window module.
Existing window modules can therefore easily be exchanged for the
present window module.
[0013] Advantageous configurations and improvements of the
invention are set out in the dependent claims.
[0014] According to a configuration, the current-generating element
is arranged in the region of the inner surface of the window frame.
The largest possible region for generating electric current can
therefore be exploited for the arrangement of the
current-generating element.
[0015] According to a further configuration, the current-generating
element generates the electric current by means of a photoelectric
element. The current-generating element can therefore for example
be a solar cell which can generate the electric current
cost-effectively during the flight.
[0016] According to a further configuration, the current-generating
element is a polymeric organic solar cell. A solar cell of this
type can be imprinted on the window frame of the window module and
has a very low thickness. At the same time, the polymeric organic
solar cell can cover substantially the entire inner surface of the
window frame, whereby a maximum possible region for generating the
electric current is available.
[0017] According to a further configuration, the geometric
configuration of the current-generating element is substantially
identical to the geometric configuration of the associated
underlying region of the window frame. Owing to this, the shape of
the current-generating element can follow the shape of the
associated region of the window frame and regions having a curved
geometry can therefore be covered by the current-generating element
and used for generating the electric current.
[0018] According to a further configuration, the window module
comprises an interface for transmitting the electric current
generated by the current-generating element to an electronic
device. In this connection, a USB interface is preferably used,
which is present on the majority of available PEDs.
[0019] According to a further configuration, means for controlling
the charging process for the electronic device and/or an electrical
storage unit are further provided on the window frame. A charge
controller for charging the electronic device can thus preferably
be provided, which interrupts charging when the available electric
current is too low or prevents the electronic device from
overcharging. The electrical storage unit can advantageously bridge
a period of time for supplying or charging the electronic device
during which a sufficient amount of electric current cannot be made
available by the current-generating element.
[0020] According to a further configuration, the interface for
transmitting the generated electric current is arranged in the
lower region of the window frame. The existing charging cable for
the electronic device can therefore also be used in the aircraft,
while the electronic device can for example be placed on the tray
table of the aircraft seat.
[0021] According to a further configuration, the window module is
of a modular construction, consisting of the individual components.
This advantageously means that, in the case of exchanging an
existing window module or retrofitting in an existing aircraft,
only the window module has to be removed as a modular component, no
functional or electrical interfaces to the aircraft infrastructure
having to be disconnected, whereby exchange or retrofitting can be
carried out rapidly and at little cost.
[0022] According to a further configuration, the thickness of the
current-generating element is considerably less than the respective
thickness of the associated region of the window frame. This
advantageously leads to the current-generating element behaving in
a resiliently flexible manner owing to its low thickness, in such a
way that the shape of the current-generating element can follow the
shape of the associated region of the window frame and regions
having a curved geometry can therefore also be covered by the
current-generating element and used for generating the electric
current.
[0023] According to a further configuration, a window pane is
further provided, of which the material properties are selected in
such a way that the absorption of the wavelength, which the energy
generation in the current-generating element causes, of the light
entering during operation is as low as possible. Owing to this, the
wavelength available for energy generation in the
current-generating element can be converted into electrical energy
in the best possible manner.
[0024] According to a further configuration, the mechanical
interfaces for connecting the window module to the aircraft or
spacecraft correspond to the mechanical interfaces which are
conventionally used for a window module. The present window module
can therefore be retrofitted in existing aircraft at little cost.
Furthermore, in this case the existing infrastructure of the
aircraft does not have to be altered for the exchange, and
therefore cost-effective retrofitting is possible.
[0025] According to a further configuration, the current-generating
element comprises lenses for focusing and amplifying the incident
light. Said lenses are preferably arranged in the region of the
outer surface of the current-generating element. Furthermore, the
material properties of the lenses are preferably selected in such a
way that the absorption of the wavelength, which the energy
generation in the current-generating element causes, of the light
entering during operation is as low as possible. Owing to this, the
wavelength available for energy generation in the
current-generating element can be converted into electrical energy
in the best possible manner.
[0026] Furthermore, an aircraft or spacecraft having at least one
window module according to the present invention is disclosed.
BRIEF DESCRIPTION OF THE DRAWINGS
[0027] The invention will be describes in detail by way of
embodiments with reference to the accompanying figures of the
drawings.
[0028] In the figures:
[0029] FIG. 1 is a perspective view of a window module according to
the invention for an aircraft; and
[0030] FIG. 2 is a schematic block diagram of a circuit arrangement
for the functional components of the window module according to the
invention.
[0031] In the figures, like reference numerals denote like or
functionally like components, unless indicated otherwise.
DETAILED DESCRIPTION
[0032] FIG. 1 is a perspective view of a window module 1 according
to the invention for an aircraft (not shown), which module
comprises a window frame 10, a window pane 50 arranged inside the
window frame 10 and a current-generating element 20.
[0033] The current-generating element 20 may be a solar cell which
is arranged in the region of the inner surface of the window frame
10. The solar cell covers the region of the inner surface of the
window frame 10 at least in portions and is preferably arranged in
the region which is illuminated most intensively or for the longest
period of time by the sun and/or the cabin illumination system
during the flight. This may be the lower region of the inner
surface of the window frame 10. Furthermore, a plurality of solar
cells is preferably arranged in the region of the inner surface of
the window frame 10 in such a way that as high an electrical power
as possible can be made available for electrically supplying the
electronic device to be charged.
[0034] In addition, the window module 1 can also comprise an
electrical storage unit (not shown) which receives the electrical
energy generated by the solar cell and stores it until the next
time the electronic device is charged.
[0035] Furthermore, the window frame 10 comprises, in the region of
the outer surface thereof, an interface 30 for transmitting the
electric current generated by the solar cell to the electronic
device. The interface 30 is preferably a standardised interface,
such as a USB interface, which lends itself in particular to PEDs.
In the region next to the interface 30, an indicator light 70 is
arranged on the window frame 10 and visually indicates to the
passenger the occurrence of a fault when the electronic device is
being charged or supplied.
[0036] A charge controller 60 is arranged on the rear face of the
window frame 10, is mounted on the window frame 10 and is not
visible when the window module 1 is installed in the aircraft cabin
since it is covered by the window frame 10. The charge controller
60 controls the charging process for transmitting the electric
current generated by the solar cell to the electronic device via
the interface 30, taking into account the electrical storage unit
if this is provided.
[0037] The window module 1 may be of a modular construction,
consisting of the above-mentioned individual components. Owing to
this, an existing window module can be advantageously exchanged for
the present window module at little cost, since the mechanical
interfaces thereof are identical to those for connecting a
conventional window module to the fuselage structure of the
aircraft. Furthermore, in the event of a defect in an electronic
component of the present window module, the module can simply be
removed and selectively replaced with a new window module or the
faulty electronic component of the present window module can be
replaced.
[0038] FIG. 2 is a schematic block diagram of a circuit arrangement
for the functional components of the window module according to the
invention. A solar cell 20 generates an electric current and
provides this to a charge controller 60. The charge controller 60
monitors the current flow to a USB interface 30. The USB interface
30 charges and/or supplies an electronic device (not shown) with
electrical energy which is generated by the solar cell 20.
[0039] The charge controller 60 is further electrically connected
to an electrical storage unit 40. If no electronic device to be
charged is connected to the USB interface 30, the electrical energy
generated by the solar cell 20 is provided to the electrical
storage unit 40 and charges it. In addition, the electrical storage
unit 40 absorbs current peaks and can provide an (auxiliary)
electric current for charging or supplying the electronic device in
a situation in which the solar cell 20 can only generate relatively
little electric current due to unfavourable light conditions.
[0040] Furthermore, an indicator light 70 is provided which is
electrically connected to the charge controller 60. The indicator
light 70 indicates to a passenger the overall operational
availability of the USB interface 30 for charging or supplying the
electronic device.
[0041] The current flow towards the USB interface 30 is monitored
by the charge controller 60 when the electronic device is charging.
If an overload occurs with respect to the amount of current which
is currently required by the electronic device, the USB interface
30 is deactivated and the occurrence of this fault is indicated to
the passenger by an associated signal at the indicator light 70. In
the event that the window module currently cannot provide enough
electric current available for charging the electronic device via
the USB interface 30, because for example the solar cell 20
currently is not receiving enough light energy, this is then also
indicated to the passenger by means of the indicator light 70.
[0042] Although the present invention has been described herein on
the basis of preferred embodiments, it is not restricted thereto,
but can be modified in various ways.
[0043] For example, the material properties of the window pane may
be selected in such a way that the absorption of the wavelength,
which the energy generation in the current-generating element
causes, of the light entering during operation is as low as
possible.
* * * * *